Vortex Model Based H? Norm Minimization Approach for Adaptive Flight Control Using Synthetic Jets

2010 ◽  
Author(s):  
Jonathan Muse ◽  
Anthony Calise ◽  
Rajeev Chandramohan
Keyword(s):  
Flight Control ◽  
Synthetic Jets ◽  
Vortex Model ◽  
Model Based ◽  
Norm Minimization ◽  
Adaptive Flight Control ◽  
Minimization Approach

scholarly journals Vortex Model Based Adaptive Flight Control Using Synthetic Jets

2009 ◽  
Author(s):  
Jonathan Muse ◽  
Andrew Tchieu ◽  
Ali Kutay ◽  
Rajeev Chandramohan ◽  
Anthony Calise ◽  
...  
Keyword(s):  
Flight Control ◽  
Synthetic Jets ◽  
Vortex Model ◽  
Model Based ◽  
Adaptive Flight Control

Correction: Adaptive Flight Control with Unknown Time-Varying Unstable Zero Dynamics

2020 ◽  
Author(s):  
Syed Aseem Ul Islam ◽  
Adam L. Bruce ◽  
Tam W. Nguyen ◽  
Ilya Kolmanovsky ◽  
Dennis Bernstein
Keyword(s):  
Flight Control ◽  
Zero Dynamics ◽  
Time Varying ◽  
Adaptive Flight Control

An H∞ Design Approach for a PID Automatic Flight Control System of a Launch Vehicle

2016 ◽  
Vol 859 ◽  
pp. 116-123
Author(s):  
Adrian Mihail Stoica ◽  
Mihaela Raluca Stefanescu
Keyword(s):  
Flight Control ◽  
Pid Controller ◽  
Design Methodology ◽  
Launch Vehicle ◽  
Proportional Integral Derivative ◽  
Flight Control System ◽  
Numerical Examples ◽  
Stability Robustness ◽  
Norm Minimization ◽  
Atmospheric Disturbances

The paper presents a design methodology for the automatic flight control of a launch vehicle. In the proposed approach the controller has a PID (Proportional-Integral-Derivative) structure but its gains are determined solving an H∞ norm minimization problem of the mapping from the atmospheric disturbances to the control amplitude and to the angle of attack of the launcher. The design methodology is illustrated by numerical examples in which both time responses and stability robustness properties of the optimal PID controller are analyzed.

High-Sideslip Model Reference Adaptive Flight Control for Aileron Locked Aircraft

2014 ◽  
Vol 651-653 ◽  
pp. 751-756
Author(s):  
Peng Fei Cheng ◽  
Cheng Fu Wu ◽  
Yue Guo
Keyword(s):  
Flight Control ◽  
Control Method ◽  
Reference Model ◽  
Sideslip Angle ◽  
Model Reference ◽  
Control Scheme ◽  
Adaptive Flight Control ◽  
Random Initialization ◽  
Model Reference Adaptive ◽  
The Given

This paper develops a high-sideslip flight control scheme based on model reference adaptive control (MRAC) to stabilize aircraft under aileron deadlock of one side. Firstly, the cascaded flight control scheme for high-sideslip straight flight is presented and how the control signals transfer is also analyzed. After that, the control structure and laws of MRAC for attitude inner-loop connected with sideslip command are designed. Finally, the control scheme is verified under a nonlinear aircraft model in conditions of no fault and one side aileron deadlock respectively. The simulation results show that when one side aileron deadlock occurs in accompany with the plant’s aerodynamic data perturbation and random initialization of controller parameters, this control method could utilize operation points of no-fault aircraft to force the faulty aircraft following the given reference model responses and finally tracking given sideslip angle command without static error robustly.

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